Control system for model airplanes



Jan. 6, 1953 SNEED 2,624,152

CONTROL SYSTEM FOR MODEL AIRPLANES Filed Jan. 25, 1947 5 Sheets-Sheet l 47 zga7 22 :5 4

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CONTROL SYSTEM FOR MODEL AIRPLANES 3 Sheets-Sheet 2 Filed Jan. 23, 1947 INVENTOR.

Kenmtifl. Snead ATTU RN EYE Jan. 6, 1953 K. D. SNEED CONTROL SYSTEM FOR MODEL AIRPLANES 3 Sheets-Sheet 13 Filed Jan. 23, 1947 35 I INVENTOR.

fifemetk .27. Snead ATTD RN EYS Patented Jan. 6, 1953 UNITED STATES PATENT OFFICE GONTROL SYSTEM FOR MODEL AIRPLANES Kenneth D. sneea, Long Beach, Calif. Application January 23, 1947, Serial No. 723,825

(ems-"17) Claims.

This invention relates to model airplanes and more particularly to control mechanisms adapted to extend to the ground by means of wires for controlling the airplane while in flight.

It is an object of the present invention to provide control mechanisms for a model airplane adapted to be propelled by a miniature engine, which are of simple construction, easy to make, and eificient in operation.

It is another object of the present invention to provide'control mechanisms for model airplanes by which a skilled operator may maneuver the plane to cause it to roll an indefinite number of times, climb or dive, loop in or out, or any combination of these maneuvers thereby to "perform any maneuver which is possiblew'ith any of the latest pursuit planes. v

For other objects and for a better understanding of the invention reference may be had to the following detailed description taken in connection with the accompanying drawing, in which Fig. l is a plan view of an airplane in three sections and connected by a tube with spaces between the sections for the control wires and the control arms and showing diagrammatically'the controlmechanisms connected respectively with the wing section and the rudder and elevator section, 1 V

Fig. 2 is a plan view of the aileron control mechanism mounted on the tube,

' Fig. 3 is a plan view of the aileron mechanism taken at an angle of ninety degrees from the angle at which the view in Fig. 2 was taken,

Fig. 4 is a fragmentary view of a portion of the tube with the stop collars thereon,

Fig. 5 is a detail view of the body sleeve which is rotatably mounted on the tube between the stop collars,

, Fig. 6 is a detail side view of the sliding sleeve having limited sliding movement on the body sleeve of Fig. 5,

Fig. '7 is a side view looking upon the elevator and rudder control mechanism,

Fig. 8 is a side view of a tube with the stop collars thereon, v

Fig. 9 is an elevational view of the body sleeve and the operating parts which are adapted to be rotatably mounted on the tube,

Fig. 10 is a side elevational view of the elevator and rudder control mechanism looking upon a plane at an angle of ninety degrees to the plane on which the view in Fig. '7 was taken,

Fig. 11 is a transverse cross-sectional view taken on the line Il-H of Fig. 10 and looking in the direction of the arrows thereof,

Fig. 12 is a detail fragmentary view of the rider block for the elevator which is operated on the airplane structure and rotates therewith. 1

Referring now to the figures, l5 represents'a model airplane having a power plant section [5, an intermediate or wing section I! and a rear or tail section Hi, all connected together by a tube or rod IS. The tube or rod [9 is rigidly attached to the interior of the sections by means of struts A, B, and C that have centrally located collars D that embrace the tube I9. The power plant section It includes an engine which drives a propeller 2|. The intermediate section I! includes wings 22 with ailerons 23. These ailerons are connected together through a linkage 24 to a single link or rider rod 25 to an aileron control mechanism 26 to be hereafter more specifically described. As seen in Fig. 1 the rider rod 25 is slidably mounted in guide blocks 25 which are fixed to the interior of the intermediate section IT. The rear or tail section i8 includes a horizontal stabilizer 21 with elevators 28 thereon and a vertical stabilizer 29 with a rudder 3i thereon. The elevators 28 and rudder 3| are respectively connected by control wires or rods 32 and 33 with an elevator and rudder control mechanism 34 carried in the rear section l8 and to be hereinafter more specifically described. The rods 32 and 33 are slidably mounted in guide blocks 32 and 33' in similar fashion to the rod 25.

Referring now particularly to Figs. 2 to 6, there is shown the aileron control mechanism 26 and the parts thereof in detail. On the tube I9 there is freely mounted a body sleeve 35. This sleeve is retained against axial displacement on thetube by stop collars 36 and 36, but the sleeve will oscillat slightly on the tube depending upon the banking of the plane during the flying thereof. On the sleeve there is mounted for limited up and down movement a sleeve 31 with a plate portion 38 thereon. This sleeve 31 is retained against rotation relative to the sleeve 35 by diametrically opposite pins 39 projecting outwardly from the exterior of the sleeve 35 into diametrically opposite elongated slots 4| extending longitudinally on the sleeve. The sleeve 31 has projections 42 extending forwardly from the plate portion 38 and at opposite sides of the sleeve 31. On the front of the sleeve 35 at 43 and 44 there are pivoted bell cranks 45 and 4'5 having portions extending longitudinally of the sleeve 35 and other portions transversely thereof. The connection of the bell cranks is made with screws at points 43 and 44 whereby the bell cranks can be pivoted. The bell cranks 45 and 46 are connected by links 41 with the cars 42 on the sliding sleeve 31. Ma-

nipulation of one bell crank will cause the sleeve 31 to be moved in one direction while manipulation of the other bell crank will cause the sleeve to be moved in the opposite direction. Connected to the outer periphery of the plate portion 38 by means of clamp jaws 49 is a rider block 49' through which by reason of the jaws 49 the plate portion can slide and to which the rod 25 is connected. As the plate portion and sleeve is moved in one direction the ailerons will be given one movement to cause a lowering of the Wings and a movement of the sleeve 31 and plate 38 in the opposite direction will cause a raising of the wings to cause the plane to ascend or descend as desired.

Fixed to the rotatable sleeve 35 is an arm with eye portions 52 and 53 On its lower end. Wires 54 extending to the ground pass through the eye portions 52 and 53 and connect respectively with the longitudinally extending portions of the bell cranks 45 and 46. When one wire is pulled one of the bell cranks will be operated and when the other wire is pulled the other bell crank will be operated. Pulling on one wire will cause tilting of the plane wings in one direction and by pulling the other wire will cause tilting of the wings in the opposite direction.

Referring now particularly to Figs. 7 to 12, there is shown in detail the elevator and rudder control mechanism 34. This mechanism is similarly connected to the tube [9 by the stop collars 56 and in such a manner as to be free to rotate thereon. A body sleeve 5! is mounted on the tube [9 and free to rotate thereon. Wobble plate 63 is mounted on body sleeve 51 by pins 59 carried in journalled brackets 6| and 62 on opposite sides of wobble plate 63. In order to permit the wobble plate to be pivoted there is provided therein an elongated central opening 64 through which the sleeve 5'! extends. This pivotal movement of the wobble plate 63 is efiected by bell cranks 66 and 61 pivoted by means of screws 68 from opposite ides of the rear end of the sleeve 51. These bell cranks are connected by links 69 with ears H at opposite sides of the pivot pins 59 and on the wobble plate 63. An arm 72 extends downwardly and has eye portions 13 and 14 thereon. Through these eye portions there extend control wires 75 which lead to the ground.

The transverse portions of the bell cranks 66 and 61 extend to the same side of the sleeve 51. If one wire '15 is pulled the wobble plate 63 will move about pins 59 and rider block 11 thrurod 32 will move the elevators 28 in one direction. If

the other wire 75 is pulled the wobble plate 63 moves in the opposite direction thus moving the elevators in the opposite direction. Since the rider block 76 is in alignment with the pivot pins 59 the movement of the plate 63 will not cause any movement of the rod 33. As the airplane is rolled by means of the ailerons 23 rider block 18 being supported by the tail section structure moves out of alignment with the pivot pins 59 and is then operated by movement of wobble plate 63. Rod 33 connecting rider block 18 to the rudder 3| transmits all control movements to the rudder.

While various changes may be made in the detail construction, such changes shall be within the spirit and scope of the present invention as defined by the appended claims.

I claim:

1. A model airplane adapted for controlled flight comprising engine, wing and rear sections, a' rod connecting the respective sections together, said wing section having ailerons, a-con- 4 trol mechanism, wires connected to said mechanism and extending to the ground for effecting the operation of the ailerons, said mechanism being rotatable upon the rod and having an arm rotatable therewith and extending outside of the sections, said control cables or wires being guided by said arm.

2. A model airplane adapted for controlled flight comprising engine, wing and rear sections, a rod connecting the respective sections together, said wing section having ailerons, a control mechanism connected to said ailerons, wires connected to said mechanism and extending to the ground for efiecting the operation of the ailerons, said mechanism being rotatable upon the rod and having an arm rotatable therewith and extending outside of the sections, and control cables or wires guided by said arm, said mechanism including a main sleeve free to rotate upon said rod, a second sleeve slidable upon the first sleeve and a plate portion on the second sleeve, a pair of hell crank levers pivotally mounted on the opposite sides of said main sleeve in diametrically opposed relation to each other, linkage connected between the bell crank levers and the slidable sleeve and plate to cause its movement along the main sleeve whereby to effect a longitudinal adjustment of the slidable sleeve, a rider block on the outer periphery of the plate portion, and linkage connected between the rider block and the ailerons, said rider block having clamp jaws for connecting said rider block to said plate portion and said jaws being adapted to permit the plate portion to rotate therethrough.

3. A model airplane adapted for controlled flight comprising engine, wing and rear sections, a rod connecting the respective sections together, said wing section having ailerons, a control mechanism connected to said ailerons, wires connected to said mechanism and extending to the ground for effecting the operation of the ailerons, said mechanism being rotatable upon the rod and having an arm rotatable therewith and extending outside of the sections, and the control wires being guided by said arm.

4. A model airplane adapted for controlled flight comprising a plurality of sections and a rod connecting the sections together, one of said sections having control elements hinged thereto, and a control mechanism journalled on the rod and operating the control elements upon the section, said control mechanism including a mainsleeve, a member connected to the main sleeve for longitudinal movement, linkage on the main sleeve and connected with the longitudinally adjustable member the latter having an Outer periphery, and means for hooking the outer periphery of the member with the control elements including a rider block loosely connected to the section and adapted to permit the periphery of the member to be passed through it after the member and the main sleeve are rotated on the rod, an arm extending to the outer side of the sections, wires guided by the arm and connected with the linkage to efl'ect the operation of said member. p

5. A model airplane adapted for controlled flight comprising engine, wing and rear sections, a rod connecting all of said sections together, a rudder and elevator pivoted upon the rear section, and control mechanism for the rudder and elevator comprising a main sleeve journalled upon the rod, a Wobble plate pivotally connected to one end of the main sleeve and adapted to be rotated with the sleeve, control linkages connected to the main sleeve and totherwobble plate to effect a tilting movement of said plate, an arm depending from the main sleeve and having guide portions, wires extending through the guide portions of the arm and connected to the linkages to effect their actuation, said Wires extending upwardly from the ground, rider elements connected to the outer periphery of the wobble plate and respectively connecting the wobble plate with the rudder and elevator, the rider elements being arranged so that a tilting of the plate will efiect the adjustment of the elevator, and a rotation of the airplane and tilting of the plate will efiect adjustment of the rudder.

KENNETH D. SNEED.

6 REFERENCES CITED The following references are of record in the file of this patent:

UNITED STATES PATENTS Number 

